Method of achieving jet separation of an un-separated flow in a divergent nozzle body of a rocket engine

a rocket engine and jet separation technology, applied in the direction of machines/engines, vessel construction, marine propulsion, etc., can solve the problems of jet separation, difficult to implement active secondary injection, and unstable position, and achieve the effect of avoiding such instability

US6996973B2Inactive Publication Date: 2006-02-14EUROPEAN SPACE AGENCY
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Patent Information

Authority / Receiving Office
US · United States
Patent Type
Patents(United States)
Current Assignee / Owner
Publication Date
2006-02-14
Estimated Expiration
Not applicable · inactive patent

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Abstract

The invention relates to a rocket engine nozzle comprising a system for controlling jet separation of the flow in the nozzle, wherein said control system exhibits a plurality of separation triggering elements (5, 10) arranged in such a way as to generate, from mutually spaced initiation points (9), distinct zones (6) of jet separation, so as to form a three-dimensional separation of the flow.The flow control system can exhibit at least two triggering elements (5, 10).
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Description

CROSS-REFERENCE TO RELATED APPLICATIONS

[0001] This is a divisional of parent application Ser. No. 09 / 534,196 filed Mar. 24, 2000, now abandoned the disclosure of which is incorporated herein.BACKGROUND OF THE INVENTION

[0002] 1. Field of the Invention

[0003] The subject of the present invention is a rocket engine nozzle, exhibiting a jet separation control system, for example a device for injecting fluid through a wall of the nozzle, so as to induce jet separation in the gases ejected by the nozzle.

[0004] An important point in the design of a launcher is the optimization of the performance of its engines. In particular, the nozzle must be designed so as to yield a maximum thrust coefficient compatible with the limits imposed by the other constraints.

[0005] The thrust coefficient C of a nozzle is an increasing function of the ratio of the exit area Ae of the nozzle to the area At of the throat of the nozzle.

[0006] For an upper stage, which is ignited outside the atmosphere, the static pressu...

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Embodiment Construction

[0044]As shown in FIG. 1, a nozzle, designated by the general label 1, exhibits a combustion chamber 2, a throat 3, and a divergent nozzle body 4 which terminates in an exit cross section 8.

[0045]Over the perimeter of the divergent portion 4 of the nozzle, and in a cross section 7 situated in a plane, perpendicular to the axis of the nozzle, where the static pressure P of the jet is substantially greater than the nozzle separation pressure Psep, are arranged injection orifices 5 able to direct radially inward a jet of a fluid, for example the combustion gases originating from the turbopumps of the engine.

[0046]The flow separation which is generated by these orifices 5, does not exhibit axial symmetry, but on the contrary it is three-dimensional. This is because each of the injection points 5, represented here as three in number and distributed uniformly at 120° around the contour of the body 4 of the nozzle, induces a region of separation 6 of the stream exiting the nozzle. Owing to...